ODAR

0386-EX-CN-2019 Text Documents

University of Massachusetts Lowell

2019-05-13ELS_229803

ELVL—2018—0045207 Rev A May 4, 2018 Orbital Debris Assessment for The CubeSats on the CRS OA—10/ELaNa—21 Mission per NASA—STD 8$719.14A

Signature Page .Yus}?f?finsop,#(nalyst, a.i. solutions, AIS2 /lotblazy lt Scott Higginbotham, MissionKfanager, NASA KSC VA—C

National Aeronautics and Space Administration John F. Kennedy Space Center, Florida Kennedy Space Center, FL 32899 ELVL—2018—0045207 Rev A Reply to Attn of: V A—H1 May 4, 2018 TO: Scott Higginbotham, LSP Mission Manager, NASA/KSC/VA—C FROM: Yusef Johnson, a.i. solutions/KSC/AIS2 SUBJECT: Orbital Debris Assessment Report (ODAR) for the ELaNa—21 Mission REFERENCES: A. NASA Procedural Requirements for Limiting Orbital Debris Generation, NPR 8715.6A, 5 February 2008 B. Process for Limiting Orbital Debris, NASA—STD—8719.14A, 25 May 2012 C. International Space Station Reference Trajectory, delivered May 2017 D. McKissock, Barbara, Patricia Loyselle, and Elisa Vogel. Guidelines on Lithium— ion Battery Use in Space Applications. Tech. no. RP—08—75. NASA Glenn Research Center Cleveland, Ohio UL Standardfor Safety for Lithium Batteries, UL 1642. UL Standard. 4th ed. Northbrook, IL, Underwriters Laboratories, 2007 Kwas, Robert. Thermal Analysis of ELaNa—4 CubeSat Batteries, ELVL—2012— 4 0043254; Nov 2012 Range Safety User Requirements Manual Volume 3— Launch Vehicles, A Payloads, and Ground Support Systems Requirements, AFSCM 91—710 V3. HQ OSMA Policy Memo/Email to 8719.14: CubeSat Battery Non—Passivation, m Suzanne Aleman to Justin Treptow, 10, March 2014 HQ OSMA Email:6U CubeSat Battery Non Passivation Suzanne Aleman to iA Justin Treptow, 8 August 2017 TechEdSat—8 Orbital Debris Assessment Report (ODAR), T8SMP—06—XS001 Rev 0, NASA Ames Research Center The intent of this report is to satisfy the orbital debris requirements listed in ref. (a) for the ELaNa—21 auxiliary mission launching on the CRS OA—10 vehicle. It serves as the final submittal in support of the spacecraft Safety and Mission Success Review (SMSR). Sections 1 through 8 of ref. (b) are addressed in this document; sections 9 through 14 fall under the requirements levied on the primary mission and are not presented here.

RECORD OF REVISIONS REV DESCRIPTION DATE 0 ODAR Submission for TJREVERB and VCC March 2018 CubeSats A Combined original submission with full ELaNa—21 May 2018 complement

The following table summarizes the compliance status of the ELaNa—21 payload mission to be flown on the OA—10 vehicle. The 13 CubeSats comprising the ELaNa—21 mission are fully compliant with all applicable requirements. Table 1: Orbital Debris Requirement Com liance Matrix Requirement Compliance Assessment Comments 4.3—la Not applicable No planned debris release 4.3—1b Not applicable No planned debris release 4.3—2 Not applicable No planned debris release 4.A4—1 Compliant On board energy source (batteries) incapable of debris—producing failure 4.4—2 Compliant On board energy source (batteries) incapable of debris—producing failure 4. 4—3 Not applicable Noplanned breakups 4.4—4 Not applicable No planned breakups 4.5—1 Compliant 4.5—2 Not applicable 4.6—1(a) Compliant ;| Worst case lifetime 3.9 yrs 4.6—1(b) Not applicable 4.6—1(c) Not applicable 4.6—2 Not applicable 4.6—3 Not applicable 4.6—4 Not applicable Passive disposal 4.6—5 Compliant 4.7—1 Compliant Non—credible risk of human casualty 4.8—1 Compliant No planned tether release under ELaNa—21 mission

Section 1: Program Management and Mission Overview The ELaNa—21 mission is sponsored by the Human Exploration and Operations Mission Directorate at NASA Headquarters. The Program Executive is Jason Crusan. Responsible program/project manager and senior scientific and management personnel are as follows: CapSat: McKale Berg, Project Manager, University of Illinois CySat 1: Rami Shoukih, Project Manager, Iowa State University KickSat—2: BJ Jaroux, Project Manager, NASA Ames Research Center HARP: Dr. J. Vanderlei Martins, Principal Investigator OPAL: Dr. Charles Swenson, Principal Investigator, Utah State Phoenix: Sarah Rogers, Project Manager, Arizona State University SPACE HAUC: Supriya Chakrabarti, Principal Investigator, University of Massachusetts—Lowell TechEdSat 8: Marcus Murbach, Project Manager, Ames Research Center TJREVERB: Michael Piccione, Principal Investigator, Thomas Jefferson High School UNITE: Glen Kissel, Principal Investigator, University of Southern Indiana Virginia CubeSat Consortium (Aeternitas, Ceres, Libertas): Mary Sandy, Principal Investigator, Virginia Space Grant Consortium

Program Milestone Schedule Task Date CubeSat Selection September15, 2017 CubeSat Delivery to NanoRacks August 20th, 2018 Launch November 175, 2018 Figure 1: Program Milestone Schedule The ELaNa—21 CubeSat complement will be launched as payloads on the OA—10 Antares launch vehicle to the International Space Station. The ELaNa—21 mission will deploy 13 pico—satellites (or CubeSats) from the International Space Station, using the NanoRacks CubeSat dispenser. Each CubeSat is identified in Table 2: ELaNa—21 CubeSats. The ELaNa—21 manifest includes: CapSat, CySat, HARP, KickSat—2, OPAL, Phoenix, SPACE HAUC, TechEdSat 8, TJREVERB, UNITE, and the three Virginia CubeSat Consortium CubeSats (Aeternitas, Ceres, and Libertas). The current launch date is projected to be November 17‘", 2018. The CubeSats on this mission range in size from a 10 cm cube to 60 cm x 10 cm x 10 cm, with masses from about 1.2 kg to 3.5 kg, with a total mass of roughly 20 kg being manifested on this mission. The CubeSats have been designed and universities and government agencies and each have their own mission goals.

Section 2: Spacecraft Description There are 13 CubeSats flying on the ELaNa—21 Mission. Table 2: ELaNa—21 CubeSats outlines their generic attributes. Table 2: ELaNa—21 CubeSats CubeSat CubeSat CubeSat Names . CubeSat size (mm) Masses Quantity (kg) CapSat 1 300 x 100 x 100 2.8 CySat 1 340 x 100 x 100 1.6 * HARP 1 368 x 100 x 100 4.1 * KickSat—2 1 300 x 100 x 100 2s * OPAL 1 368 x 100 x 100 5.0 Phoenix 1 325 x 100 x 100 3.2 SPACE HAUC 1 340 x 100 x 100 2.9 *TechEdSat 8 1 600 x 100 x 100 7.9 TJREVERB 1 227 x 100 x 100 2.6 UNITE 1 340 x 108 x 108 3.5 VirginiaCC Aeternitas — 1 113 x 100 x 78© 1.2 Virginia Ceres CC — 1 113 x 106 x 106 1.2 Virginia CC — Libertas 1 118 x 105 x 106 1.4 *The following pages describe the CubeSats flying on the ELaNa—21 mission, with the omissions noted below. ODARs for these CubeSats were previously submitted to the Agency as follows: HARP: ELaNa—22 Rev A ODAR 5/2017 KickSat—2: KickSat—2 9/2015 OPAL: ELaNA—22 ODAR 10/16 TechEdSat—8‘s ODAR was drafted by NASA Ames (Document No. T8SMP—06— XS001 Rev 0)

SPACE HAUC — University of Massachusetts, Lowell — 3U Comume. Nysteni sSoliar Poanels ‘;\~ Ebrermank a Fneufadion L & Soruetiorn«e Conmeris Figure 5: SPACE HAUC Expanded View Overview SPACE HAUC will demonstrate that high data transmission rates can be achieved by using a X—Band Phased—Array antenna with an electronically steered beam on a CubeSat. CONOPS Immediately upon deployment, SPACE HAUC will power up and determine if it is spin stabilized. If not, the Attitude Determination and Control System will stabilize the spin. It will then determine if it is sun pointed, if not the Attitude Determination and Control System will point SPACE HAUC at the sun. SPACE HAUC will then wait for a beacon signal from the ground, upon receipt of the beacon, SPACE HAUC will take pictures of the sun and transmit them down. The process of waiting for the beacon signal will be repeated whenever the beacon signal is lost. Materials The CubeSat structure is made of Aluminum 7075—T6. It contains all standard commercial off the shelf (COTS) materials, electrical components, PCBs and solar cells except for the RF front end board and patch antennas which are custom designed. The high—speed radio uses a ceramic patch antenna. 15

Hazards There are no pressure vessels, hazardous, or exotic materials. Batteries The lithium—ion battery is charged with all the available power from the photo—voltaic inputs that is not drained by the loads on the external power busses. The battery is protected against voltage being too high or too low. The software high voltage protection implements a constant voltage charge scheme that will keep the battery at its maximum voltage. The full mode regulation works by lowering voltage on the solar panel inputs, thereby only taking in the power needed. The software low voltage protection is a four state system. Should the battery voltage drop below 7.2 V, the battery hardware will switch to a ‘safe mode‘ configuration, which allows for the switching off of all essential systems and leaves only a simple power beacon running. Should the battery drop below 6.5 V, the software will switch off all user outputs. 16

Section 3: Assessment of Spacecraft Debris Released during Normal Operations The assessment of spacecraft debris requires the identification of any object (>1 mm) expected to be released from the spacecraft any time after launch, including object dimensions, mass, and material. The section 3 requires rationale/necessity for release of each object, time of release of each object, relative to launch time, release velocity of each object with respect to spacecraft, expected orbital parameters (apogee, perigee, and inclination) of each object after release, calculated orbital lifetime of each object, including time spent in Low Earth Orbit (LEO), and an assessment of spacecraft compliance with Requirements 4.3—1 and 4.3—2. No releases are planned on the ELaNa—21 CubeSat mission therefore this section is not applicable. 27

Section 4: Assessment of Spacecraft Intentional Breakups and Potential for Explosions. There are NO plans for designed spacecraft breakups, explosions, or intentional collisions on the ELaNa—21 mission. The probability of battery explosion is very low, and, due to the very small mass of the satellites and their short orbital lifetimes the effect of an explosion on the far—term LEO environment is negligible (ref (Lh)). The CubeSats batteries still meet Req. 56450 (4.4—2) by virtue of the HQ OSMA policy regarding CubeSat battery disconnect stating; "CubeSats as a satellite class need not disconnect their batteries if flown in LEO with orbital lifetimes less than 25 years." (ref. (b)) Limitations in space and mass prevent the inclusion of the necessary resources to disconnect the battery or the solar arrays at EOM. However, the low charges and small battery cells on the CubeSat‘s power system prevents a catastrophic failure, so that passivation at EOM is not necessary to prevent an explosion or deflagration large enough to release orbital debris. The 6U CubeSat in this complement satisfy Requirements 4.4—1 and 4.4—2 if their batteries at equipped with protection circuitry, and they meet International Space Station (ISS) safety requirements for secondary payloads. Additionally, these CubeSats are being deployed from a very low altitude (ISS orbits at approximately 400 km), meaning any accidental explosions during mission operations or post—mission will have negligible long—term effects to the space environment. Assessment of spacecraft compliance with Requirements 4.4—1 through 4.4—4 shows that with a maximum CubeSat lifetime of 3.9 years maximum, the ELaNa—21 CubeSats are compliant. 28

Section 5: Assessment of Spacecraft Potential for On—Orbit Collisions Calculation of spacecraft probability of collision with space objects larger than 10 cm in diameter during the orbital lifetime of the spacecraft takes into account both the mean cross sectional area and orbital lifetime. The largest mean cross sectional area (CSA) among the 13 CubeSats is that of the SPACE HAUC CubeSat with solar arrays deployed. Comm. Systom Solar Panels Camera Figure 10:; SPACE HAUC Expanded View (with solar panels deployed) Mean CSA = ZSurftzce Area _ [2 * {(w * I) -;4 * (w * A)] Equation 1: Mean Cross Sectional Area for Convex Objects A + Aq + A Mean CSA = g_’%__l) Equation 2: Mean Cross Sectional Area for Complex Objects All CubeSats evaluated for this ODAR are stowed in a convex configuration, indicating there are no elements of the CubeSats obscuring another element of the same CubeSats from view. Thus, the mean CSA for all stowed CubeSats was calculated using Equation 1. This configuration renders the longest orbital life times for all CubeSats. Once a CubeSat has been ejected from the NanoRacks dispenser and deployables have been extended, Equation 2 is utilized to determine the mean CSA. Amax is identified as the view that yields the maximum cross—sectional area. A1 and A; are the two cross— sectional areas orthogonal to Amax. Refer to Appendix A for component dimensions used in these calculations The SPACE HAUC (2.9 kg) orbit at deployment is 408 km apogee altitude by 400 km perigee altitude, with an inclination of 51.6 degrees. With an area to mass ratio of 0.00398 m*/kg, DAS yields 3.9 years for orbit lifetime for its stowed state, which in turn 29

is used to obtain the collision probability. Even with the variation in CubeSat design and orbital lifetime ELaNa—21 CubeSats see an average of 0.0 probability of collision. All CubeSats on ELaNa—21 were calculated to have a probability of collision of 0.0. Table 3 below provides complete results. There will be no post—mission disposal operation. As such the identification of all systems and components required to accomplish post—mission disposal operation, including passivation and maneuyvering, is not applicable. 30

CubeSat CapSat CySat Phoenix SPACE HAUC TechEdSat 8 Mass (kg) 2.8 2.7 3.2 2.9 7.9 Mean C/S Area (m42) 0.282 0.018 0.015 0.0116 0.104 -§ Area—to Mass (m42/kg) 0.102 0.014 0.012 0.004 0.0132 g Orbital Lifetime (yrs) 0.23 3.4 3.7 3.9 2.2 Probability of collision (10X) 0.00000 0.00000 0.00000 0.00000 0.00000 % % Mean C/S Area (m42) 0.0709 0.564 3 & > Area—to Mass (m4*2/kg) 0.0243 0.0714 2 Orbital Lifetime (yrs) 1.09 0.482 a. o o Probability of collision (104X) 0.00000 0.00000 Solar Flux Table Dated 8/14/2017 **Note: Blacked out areas represent CubeSats which do not have deployables or have deployable antennae with negligible areas with respect to on—orbit dwell time calculation. Data for TechEdSat—8 taken from Ames— submitted ODAR report. 31

Table 3: CubeSat Orbital Lifetime & Collision Probability TJREVERB CubeSat UNITE Aeternitas Ceres Libertas Mass (kg) 2.6 3.5 1.2 1.2 1.4 Mean C/S Area (m42) 0.085 0.020 0.0163 0.0176 0.0182 C Area—to Mass (m4~2/kg) 0.0327 0.006 0.0136 0.0147 0.0130 3 Orbital Lifetime (yrs) 0.77 3.4 2.3 2.0 2.4 a § = — r°bab"(':‘(’)f;)°°"'s'°" 0.00000 0.00000 0.00000 0.00000 0.00000 x Mean C/S Area (m42) * 3 Area—to Mass (m42/kg) 5 |__Orbital Lifetime (yrs) §' Probability of collision (10"X) Table 3: CubeSat Orbital Lifetime & Collision Probability (cont.) 32

The probability of any ELaNa—21 spacecraft collision with debris and meteoroids greater than 10 cm in diameter and capable of preventing post—mission disposal is less than 0,00000, for any configuration. This satisfies the 0.001 maximum probability requirement 4.5—1. The VCC CubeSat Aeternitas will deploy a petal—like drag brake, for the purpose of providing data regarding drag effects upon its orbit. This feature does not increase the probability of on—orbit collision. The ELaNa—21 CubeSats have no capability or plan for end—of—mission disposal, therefore requirement 4.5—2 is not applicable. In summary, assessment of spacecraft compliance with Requirements 4.5—1 shows ELaNa—21 to be compliant. Requirement 4.5—2 is not applicable to this mission. Section 6: Assessment of Spacecraft Post Mission Disposal Plans and Procedures All ELaNa—21 spacecraft will naturally decay from orbit within 25 years after end of the mission, satisfying requirement 4.6—1a detailing the spacecraft disposal option. Planning for spacecraft maneuvers to accomplish post—mission disposalis not applicable. Disposal is achieved via passive atmospheric reentry. Calculating the area—to—mass ratio for the worst—case (smallest Area—to—Mass) post— mission disposal among the CubeSats finds SPACE HAUC in its stowed configuration as the worst case. The area—to—mass is calculated for is as follows: Mean C/SArea (m") a m m W = Area — to — Mass (7('5) Equation 3: Area to Mass 0.0116 m = o 004m2 2.9kg _ kg SPACE HAUC has the smallest Area—to—Mass ratio and as a result will have the longest orbital lifetime. The assessment of the spacecraft illustrates they are compliant with Requirements 4.6—1 through 4.6—5. DAS 2.1.1 Orbital Lifetime Calculations: DAS inputs are: 408 km maximum apogee 400 km maximum perigee altitudes with an inclination of 51.6° at deployment no earlier than April 2018. An area to mass ratio of ~0.004 m*/kg for the SPACE HAUC CubeSat was used. DAS 2.1.1 yields a 3.9 years orbit lifetime for SPACE HAUC in its stowed state. This meets requirement 4.6—1. For the complete list of CubeSat orbital lifetimes reference Table 3: CubeSat Orbital Lifetime & Collision Probability. Assessment results show compliance. 33

Section 7: Assessment of Spacecraft Reentry Hazards A detailed assessment of the components to be flown on ELaNa—21 was performed. (Data provided for TechEdSat—8 in their submitted ODAR report was reviewed as well). The assessment used DAS 2.1.1, a conservative tool used by the NASA Orbital Debris Office to verify Requirement 4.7—1. The analysis is intended to provide a bounding analysis for characterizing the survivability of a CubeSat‘s component during re—entry. For example, when DAS shows a component surviving reentry it is not taking into account the material ablating away or charring due to oxidative heating. Both physical effects are experienced upon reentry and will decrease the mass and size of the real—life components as the reenter the atmosphere, reducing the risk they pose still further. An assessment of the components flown on TechEdSat—8 is contained in Reference J. The following steps are used to identify and evaluate a components potential reentry risk relative to the 4.7—1 requirement of having less than 15 J of kinetic energy and a 1:10,000 probability of a human casualty in the event the survive reentry. 1. Low melting temperature (less than 1000 °C) components are identified as materials that would never survive reentry and pose no risk to human casualty. This is confirmed through DAS analysis that showed materials with melting temperatures equal to or below that of copper (1080 °C) will always demise upon reentry for any size component up to the dimensions of a 1U CubeSat. 2. The remaining high temperature materials are shown to pose negligible risk to human casualty through a bounding DAS analysis of the highest temperature components, stainless steel (1500°C). If a component is of similar dimensions and has a melting temperature between 1000 °C and 1500°C, it can be expected to possess the same negligible risk as stainless steel components. Table 4: ELaNa—21 High Melting Temperature Material Analysis WCluIbd LGrSie CubeSat Name EU bicICue) Total Mass (ke) Alt (km} mt CAPSat Antennae Stainless Steel 0176 0 0 CAPSat Pointing Panel 301 Stainless Steel 0382 0 10 CAPSat Face Sealldee Connector 316 Stainless Steel 0093‘ 717.5 0 CAPSat Gear Pump 316 Stainless Steel 110 68.6 0 CAPSat Bellows Accumulator 316 Stainless Steel .218 63.8 0 CAPSat Pressure Sensors 316 Stainless Steel .079 : 70.3 0 CAPSat Radiator Panel Hinge Unfinished Steel 0068 76.5 0 Radi B CAPSat adiator Board Standoffs 18—8 Stainless Steel 0055 73.8 0 CAPSat Pipe Fittings Stainless Steel (generic) various 75.2 o CySat Rods Stainless §teel :080 o o (generic) CySat Standoffs sones Sfls .084 72.8 0 {generic) 34

CySat Fasteners Soe .StEEI .040 77.0 0 {generic) ® _ Stainless Steel CySat Separation Switches (generic} .028 0 0 CySat RBF Pin sseen (generic} .017 74.7 o e . Stainless Steel CySat Separation Springs ces 0002 77.3 0 CySat Reaction Wheel Brass .060 73.1 0 Stainless Steel CySat Magnetometer t(generic) 005 77.3 0 CySat Deployable Stainless §teel 002 97.8 o Magnetometer (generic} Phoenix Screws Snsce (generic) 6.94 77.7 0 Phoenix Nuts Stainless Steel {generic) 3.92 77.6 o Phoenix Electronics Stack Rod Stainless §tee| 4,29 76.8 0 {generic) Phoenix Separation Springs Stainless §tee| 0.072 77.9 0 (generic) SPACE HAUC Torsion Spring Steel (AIS! 304) 00015 778 l _0 SPACE HAUC 4—40 Screws Steel {A1§1304} .004 \T6r "|| o SPACE HAUC Spacer RF Boards Steel {AISI304) .004 765_ 0 TIREVERS Standoff screws Stainless Steel (generic) .020 77.7 o TIREVERR 6 mm screws Stainless Steel (generic) .064 77.5 0 UNITE External Fasteners sunestateS :020 77.6 _ o. {generic) , P . UNITE Magnet Haider Lexan _ .010 ~78.0 0 — ) unite Mu—Metal Rod s {nickel alloy) 047 F43 Mk 714. L. 0 UNITE Internal Fasteners eoesshee {generic) 0002 Gers 7e * is n o Virginia CC: Aeternitas Antenna Blades Steel/copper plate 0005 0 0 Vvirginia CC: Separation Switches Beryllium Copper .003 ‘ 0 0 Ceres Virginia CC: Solar Pangl Retaining Stainless Steel .oo1 o o Ceres Clips Virginia CC: Magnet Mounting Aluminum .050 o o Ceres Plates Virginia CC: Separation Switches Beryllium Copper 003 0 0 Libertas P ery ppe " The majority of stainless steel components demise upon reentry and all CubeSats comply with the 1:10,000 probability of Human Casualty Requirement 4.7—1. A breakdown of the determined probabilities follows: 35

Table 5:; Requirement 4.7—1 Compliance by CubeSat Risk of Human Name Status yeet CapSat Compliant 1:0 CySat Compliant 1:0 SPACE HAUC Compliant 1:0 TechEdSat—8 Compliant 1:0 TJIREVERB Compliant 1:0 UNITE Compliant 1:0 Virginia . . CC:Aeternitas Coinpliant 1:0 Virginia CC: Compliant 1:0 Ceres Virginia CC: & . Libertas Compliant 1:0 *Requirement 4.7—1 Probability of Human Casualty > 1:10,000 If a component survives to the ground but has less than 15 Joules of kinetic energy, it is not included in the Debris Casualty Area that inputs into the Probability of Human Casualty calculation. This is why all of the ELaNa—21 CubeSats have a 1:0 probability as none of their components have more than 15J of energy. All CubeSats launching under the ELaNa—21 mission are shown to be in compliance with Requirement 4.7—1 of NASA—STD—8719.14A. 36

Section 8: Assessment for Tether Missions ELaNa—21 CubeSats will not be deploying any tethers. ELaNa—21 CubeSats satisfy Section 8‘s requirement 4.8—1. 37

Section 9—14 ODAR sections 9 through 14 pertain to the launch vehicle, and are not covered here. Launch vehicle sections of the ODAR are the responsibility of the CRS provider. If you have any questions, please contact the undersigned at 321—867—2098. /original signed by/ Yusef A. Johnson Flight Design Analyst a.1. solutions/KSC/AIS2 ce: VA—H/Mr. Carney VA—H1/Mr. Beaver VA—H1/Mr. Haddox VA—C/Mr. Higginbotham VA—C/Mrs. Nufer VA—G2/Mr. Treptow SA—D2/Mr. Frattin SA—D2/Mr. Hale SA—D2/Mr. Henry Analex—3/Mr. Davis Analex—22/Ms. Ramos 38

Appendix Index: Appendix A. ELaNa—21 Component List by CubeSat: CAPSat Appendix B. ELaNa—21 Component List by CubeSat: CySat Appendix C. ELaNa—21 Component List by CubeSat: Phoenix Appendix D. ELaNa—21 Component List by CubeSat: SPACE HAUC Appendix E. ELaNa—21 Component List by CubeSat: TJREVERB Appendix F. ELaNa—21 Component List by CubeSat: UNITE Appendix G. ELaNa—21 Component List by CubeSat: Virginia CC: Aeternitas Appendix H. ELaNa—21 Component List by CubeSat: Virginia CC: Ceres Appendix I. ELaNa—21 Component List by CubeSat: Virginia CC: Libertas Appendix J. ELaNa—21 TechEdSat—8 ODAR (produced by NASA—Ames) 39

Appendix D. ELaNa—21 Component List by CubeSat: SPACE HAUC T | er | yee j tm Aat seetuelas ~) SpaceHAUC 3U CubeSat 2 Spacecraft Bus Side 2 Aluminum 7075—T6 Box 266.62 82.2 337 2.83 No — Demise 3 Solar Panel Frame 4 Aluminum 7075—T6 Panel 308.72 95 96 9.175 No — Demise 4 Camera Plate 1 Aluminum 7075—T6 Plate 71.69 10 64 10 No — Demise 5 Hinge Base 4 Aluminum 7075—T6 Box 25.08 20 34 5 No — Demise 6 Hinge Rotor 4 Aluminum 7075—T6 Plate 18.12 2.02 37.5 N/A No — Demise 7 Hinge Pin 4 Aluminum 7075—T6 Pin 1.68 0.305 19.34 N/A No — Demise s 1800 Torsion Spring 4 Alst 32‘;3;““'“3 Spring 01528 0.0382 orszs 0.305 No 2550° Demise 9 4—40 Screws AIs1 304Stainless Bolt 0 6.35 25 8.5 No 2550° Demise 10 Dowel Holster 4 Aluminum 7075—T6 Box 9.172 3.175 27.94 N/A No — Demise 11 Dowel 4 Aluminum 7075—T6 Pin 2.192 A.16 1.59 N/A No — Demise 12 Dowel Hex Nut s ABBQd Nut 14712 144 127 4.57 No — Demise 13 Compression Spring 4 AISI 3(;13e21tainless Spring 0.4684 82.6 326 2.3 No — Demise 14 Solar Panels 4 Commercial FR4 Panel 624 ~ 95 96 5 No — Demise 15 EPS Front Mount 1 Aluminum 7075—T6 Plate 81.53 95 96 5 No Demise 16 EPS Back Mount 1 Aluminum 7075—T6 Plate 78.24 92.92 93.39 36.75 No — Demise 17 E’e"""“ic(gf‘,’;;"" Supply 1 Commercial FR4 Box 100 93.34 g7144 28.71 No — Demise 18 Battery Pack 1 Glass/Polymide Box 270 6.35 16.26 1245 No — Demise 19 Deployment Switch 2 Box 4 No — Demise 20 Wires 1 Copper Wires 20 14 27.4 5.9 No — Demise 21 NanoSSOC—A60 Sensor Fine Sun 1 Box 4 16.51 19.05 1.63 No — Demise 22 TSL2561 Coarse Sun Sensor 8 Chip 24 95 96 10 No — Demise 47

23 Magnetorquer Board 1 Aluminum 7075—T6 Plate 98.22 8.5 70 N/A No — Demise 24 Magnetorquer Rods 3 Copper Cylinder 90 6 20 6.5 No — Demise 25 Magnetorquer Rod Collar 4 Aluminum 7075—T6 Box 5.2 22.86 33.02 2.36 No — Demise 26 9]\}[1(;:efi,‘:sng 1 Commercial FR4 Chip 2.8 62 100 11.73 No — Demise 27 ADRVI361 1 Board 60 76.2 1524 6.65 No — 28 ADRVI361 Breakout Board Demise 1 Board 80 54 92 1.57 No — Demise 29 Auxilary Mounting Board 1 Aluminum 7075—T6 Plate 26.94 88 144 1.57 No — Demise 30 Base Board 1 Aluminum 7075—T6 Plate 64.09 30 30 41.2 No Demise 31 Camera 1 Cylinder 21 2.5 22 N/A No — 32 Demise Standoff_Camera 4 Aluminum 7075—T6 Cylinder 0448 6 6.93 20 No — Demise 33 Standoff_ADRV 8 Cylinder 84 95 96 8 No — Demise 34 Tape Antenna Base 1 Aluminum 7075—T6 Plate 114.54 95 96 10 No — Demise 35 Antenna Mounting Brace 1 Aluminum 7075—T6 Plate 123.67 95 96 1.57 No — Demise 36 Back End Board 1 RO4000 Board 35 95 96 1.57 No — Demise 37 Daughter Board 1 RO4000 Board 35 95 96 1.57 No — Demise 38 Patch Antenna 1 RO4000 Board 14 16 23.6 4.74 No — Demise 39 Tape Cage_Mo nopole 2 Aluminum 7075—T6 Plate Antenna 1.5 22 9 N/A No — Demise 40 Pulley_Monopole Antenna 2 Aluminum 7075—T6 Cylinder 10.76 4.5 5 4.5 No — Demise 41 Spacer_RF Boards 8 AISI 3g‘t‘egltai“'ess Cylinder 4312 Yes 2550° Demise 42 Wires 1 Copper Wires 20 100 340 0.2 No = Demise 43 Multi—Layer Insulation 1 Insulation Panel 40 No — Demise 44 Radiators 2 Aluminum 7075—T6 Panel 150 N/A N/A N/A No — Demise 45 Paints 1 AZ—93 White Paint Paint 5 100 340 12 No — Demise 48


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Document Modified: 2018-11-07 00:38:10
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